Interaction of aerospike nozzle flows with external flows

• Applicant: Dr. Sven Scharnowski
• Subject Area: Fluid Mechanics
• Term: since 2021
• Project identifier: Deutsche Forschungsgemeinschaft (DFG) - Project number 464275368

The aero-spike nozzle represents a promising alternative to current rocket thrust nozzles for future space systems. In contrast to the classic bell nozzle, it has a variable expansion ratio and does not require any moving elements. This theoretically improves both the reliability and the efficiency of the transport of satellites into their orbits with launchers. However, in order to enable the use of aerospike nozzles in the future, further fundamental investigations in various fields of research are necessary. In the project applied for here, fundamental questions regarding the aerodynamic integration of an aerospike nozzle into the rear of a launcher are to be investigated. In the Trisonic Wind Tunnel Munich, experiments will be carried out on a generic rocket model with a linear aero-spike nozzle with a cold jet at different flow conditions. A special focus of the investigations will be the characterization of the dynamics of the propulsion jet as well as the detached flow in the rear area of the rocket and their interaction with each other. Furthermore, geometry variations of the central body and the primary nozzles will be investigated, which will allow the suitability of different concepts to be examined and evaluated. For this purpose, state-of-the-art optical flow measurement methods will be further developed and applied to collect pressure and velocity data relevant for the evaluation. It is expected that the project results will contribute significantly to the fundamental understanding of the dynamics of aerospike nozzle flows and thus may help to improve future propulsion systems.

• DFG Programme: Research Grants